TCDS A17WE

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Rev. No. 23 21 21 21 21 22 21 21 22 21 22 21 22 22 22 22 Page No. 17 Rev. No. 21 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINSTRATION A17WE Revision 23 Aerostar PA-60-600 (Aerostar 600) PA-60-601 (Aerostar 601) PA-60-601P (Aerostar 601P) PA-60-602P (Aerostar 602P) PA-60-700P (Aerostar 700P) September 24, 2012 TYPE CERTIFICATE DATA SHEET NO. A17WE This data sheet, which is a part of Type Certificate A17WE, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the Airworthiness Requirements of the Federal Aviation Regulations. Holder of Type Certificate: Aerostar Aircraft Corporation 10555 Airport Drive Coeur d'Alene Airport Hayden Lake, ID 83835 I. Aerostar Model PA-60-600 (Aerostar 600) (Normal Category) Approved March 28, 1968 (See Note 2 & 4) Engines: Two Lycoming IO-540-G1B5, IO-540-K1F5, IO-540- K1J5 (with Bendix fuel injector servos 2524491- ); IO-540-S1A5 or IO-540-P1A5 (wit h Bendix fuel injector servos 2524491- ). NOTE: IO-540-S1A5 or IO-540-P1A5 engines are optional and installed per AAC Option 35. Fuel: 100/130 and 100LL minimum grade aviation gasoline Engine Limits: *2575 RPM. 29.5 in. Hg. MAP (290 HP) for all operations **2575 RPM, 29.5 in. Hg. MAP (290 HP) Maxi mum Continuous Power for takeoff, obstacle clearance, and emergency operations only. (No time limit.) 2520 RPM, 29.5 in. Hg. MAP (284 HP) Maximum Normal Operating Power for noise certification and fo r all other operations. (See "Noise Characteristics" paragraph) *For S/N 60-0001 thru 60-0714-7961221 **For S/N 60-0715-8061222 and subsequent Propeller Two Hartzell full-feathering propellers - HC-C3YR-2/C8468-8R or HC-C3YR-2UF/FC8468-8R. Propeller Limits (a) Pitch setting at 30 in. sta. Low 14° + 0.1°, High 18° -21° Feather 82.5° + 1.0° Diameter: 78 inches No cutoff for repairs permitted. (b) Spinners - Hartzell C-3258P (c) Propeller Governor - Hartzell F-6-5A , F-6-35, F-6-35Z, F-6-36, F-6-36Z, F-8-35, F-8-35Z, F-8-45, or F-8-45Z. A17WE 2 NOTE: If modified in accordance with AAC Option 64, Synchrophaser, Governor for right engine is F-8-35 or F- 8-35Z. If modified in accordance with AAC Op tion 150, Synchrophaser, Governor for right engine is F-8-45 or F-8-45Z. Airspeed Limits: (See Note 2) V ne- Never exceed 243 KCAS (280 MPH) V no- Max. structural cruising 217 KCAS (250 MPH) V a- Max. design maneuvering 163 KCAS (188 MPH) V fe- *Flaps extended 20° 156 KCAS (180 MPH) 45° 130 KCAS (150 MPH) - **Flaps extended 20° 174 KCAS (200 MPH) 45° 149 KCAS (172 MPH) V le-Max. gear extended 156 KCAS (180 MPH) V lo-Max gear retraction 130 KCAS (150 MPH) -Max gear extension 156 KCAS (180 MPH) *For S/N 60-0001 thru 60- 0014, 60-0015-26 thru 60-0056-128, 60-0130-057 thru 60-0355-127. The flap speeds for these S/N aircraft may be increased from 130 KCAS and 156 KCAS to 149 KCAS and 174 KCAS respectively when modified in accordance with AAC Option No. 131. **For S/N 60-0359-128 and subsequent. C.G. Range LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 lbs. 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (3) 60-0001 thru 4600 157.66 (12.2% MAC) 167. 88 (28.5% MAC) (3) 60-0824-8061236 5500 159.58 (15% MAC) 167.88 (28.5% MAC) 5500 159.58 (15% MAC) 166.00 (25.5% MAC) (2) (3) LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (3) 60-0833-8161237 4600 157.66 (12.2% MAC) 167. 88 (28.5% MAC) and subsequent 5500 159.58 (15% MAC) 167.88 (28.5% MAC) 5525 159.63 (15.1% MAC) 167.88 (28.5% MAC) 5500 159.58 (15% MAC) 166.00 (25.5% MAC) (2) (3) 5525 159.63 (15.1% MAC) 166. 00 (25.5% MAC) (2) (3) (1) Straight line variat ion between weight points. (2) For aircraft equipped for Flight into Known Icing AAC Option No. 196. (3) For aircraft with Aerostar Ki t 764 969V (ventral rudder) installed. Empty Weight NONE C.G. Range Maximum Weight 5525 lbs. MA X RAMP (60-0833-8161237 and subsequent). 5500 lbs. MAX. TAKEOFF 3 A17WE No. of Seats Crew or Fuselage Passenger Station 2 96 (CREW) 2 132 2 165* *When bench seat is fitted, three occupants may be accommodated provided that the maximum weight of 380 lbs. is not exceeded. See Flight Manual for loading instructions. Maximum Baggage (See Note 2) Rear compartment 240lbs. at (+245) Fuel Capacity Wing Total Capac ity (65 gals. each)........ 130 gals. Wing Total Usable ( 62 gals each)........... 124 gals. Fuselage Total C apacity............................ 43.5 gals. Fuselage Total Usable............................ 41.5 gals. Aircraft Total C apacity................................. 173.5 gals. Aircraft Total Usable................................. 165. 5 gals. (See Note 1 for unusable fuel) Oil Capacity Total Capacity tw o engines @ sta. +145.... 24 qts. Capacity each engine @ sta. +145.............. 12 qts. Usable each engi ne....................................... 9 1/4 qts. (See Note 1 for undrainable oil) Control Surface Movement Wing Flaps* Down 45 °+ 3° Main Surfaces Aileron** Up 25° + 1° Down 15° + 1° Elevator Up 30° + 1° Down 10° + 1° Rudder Right 30° + 1° Left 30° + 1° ***Right 35° + 1° - 0 ° Tabs (Main surface in neutral) Elevator Up 7°+ 1° Down 37° +9° - 1 ° Rudder Right 9° + 4° Left 37° + 4° - 1 ° - 1 ° *Flaps must be rigged so that at 20° flap setti ng, R.H. flap must not be more 1.0° lower or 4.0° above the L.H. flap. **Ailerons are rigged 2° down. Mo vements are measured from this neutral position. Elevator and rudder movements are m easured from a faired neutral position. ***For aircraft with Aerostar Kit 764 969V (ventral rudder) installed. Serial Numbers 60-0001 thru 60-0014, 60-0015- 26 thru 60-0056-128, 60-0130-057 thru 60-0933-8161262, Eligible 60-8261001 and subsequent. (See Note 4) A17WE 4 II Aerostar Model PA-60-601 (AEROSTAR 601) (Normal Category) Approved November 8, 1968. (See Note 2 and 4) Engines Two Lycoming IO-540-P1A5, IO-540-S1A5 or IO-540-G1B5 modified to incorporate turbochargers in accordance with RAJAY ST C SE6WE with Bendix fuel injector servos. 2524477 - for S/N 61-0001 thru 61-0334-111* and 2524491 - for S/N 61-0342-112 and subsequent *These aircraft require P/N 2524491 Bendi x fuel injector servos when modified in accordance with AAC Option 93. Fuel 100/130 and 100LL minimum grade aviation gasoline. Engine Limits *2575 RPM, 29.5 in. Hg. MAP (290 HP) for all operations. **2575 RPM, 29.5 in. Hg. MAP ( 290 HP) Maximum Continuous Power for takeoff, obstacle clearance, and emergency operati ons only. (No time limit). 2475 RPM, 29.5 in. Hg. MAP (278 HP) Maximum Normal Operating Power for noise certification and fo r all other operations. (See "Noise Characteristics" paragragh). *For S/N 61-0001 thru 61-0714-7962143 and 62-001 **For S/N 61-0715-8062144 and subsequent. Propeller Two Hartzell full-feathering propellers - HC- C3YR-2/C8468-8R or HC-C3YR-2UF/FC8468-8R. Propeller Limits a.) Pitch settings at 30 in. sta. Low 14°+ 0.1°, High 18° -21° Feather 82.5°+ 1.0° Diameter: 78 inches No cutoff for repairs permitted. b.) Spinners - Hartzell C-3258P c.) Propeller Governor - Hartzell F-6-5A, F- 6-35, F-6-35Z, F-6-36, F-6-36Z, F-8-35, F-8- 35Z, F-8-45, F-8-45Z. NOTE: If modified in accordance with AAC Option 64, Synchrophaser, Governor for right engine is F-8-35 or F-8-35Z. If modified in accordance with AAC Option 150, Synchrophaser, Governor for right engine is F-8-45 or F-8-45Z. Airspeed Limits (See Note 2) V ne- Never exceed 243 KCAS (280 MPH) V no- Max. structural cruising 217 KCAS (250 MPH) Reduce V ne and Vno (5 MPH) 4 knots for each 1,000 feet above 24,000 feet. V a- Max. design maneuvering 167 KCAS (192 MPH) V fe- *Flaps extended 20° 156 KCAS (180 MPH) 45° 130 KCAS (150 MPH) - **Flaps extended 20° 174 KCAS (200 MPH) 45° 149 KCAS (172 MPH) V le-Max. gear extended 156 KCAS (180 MPH) V lo-Max gear retraction 130 KCAS (150 MPH) -Max gear extension 156 KCAS (180 MPH) 5 A17WE *For S/N 61-0001 thru 61-0352-114 and 62-001. The flap speeds for these S/N aircraft may be increased from 130 KCAS and 156 KCAS to 149 KCAS and 174 KCAS respectively when modified in accordance with AAC Option No. 131. **For S/N 61-0357-115 and subsequent. C.G. Range LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 lbs. 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (6) 61-0001 thru 4600 157.66 (12.2% MAC) 167.88 (28. 5% MAC) 61-0334-111 and 5700 160.03 (15.7% MAC) 167.88 ( 28.5% MAC) 62-001 5700 160.03 (15.7% MAC) 166. 00 (25.5% MAC) (5) (4) (6) 4600 157.66 (12.2% MAC) 166.00 (25.5% MAC) (6) 61-0342-112 thru 4600 157.66 (12.2% MAC) 167.88 (28.5% MAC) 61-0806-8062151 6000 160.67 (17% MAC) 167.88 (28.5% MAC) 6000 160.67 (17% MAC) 166.00 (25.5% MAC) (5) (2) (6) 4600 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (6) 61-0838-8162152 4600 157.66 (12.2% MAC) 167.88 (28.5% MAC) and subsequent 6000 160.67 (17% MAC) 167.88 (28.5% MAC) 6025 160.72 (17.1% MAC) 167.88 (28.5% MAC) 6000 160.67 (17% MAC) 166.00 (25.5% MAC) (5) (6) 6025 160.72 (17.1% MAC) 166.00 (25.5% MAC) (5) (6) (1) Straight line va riation between points. (2) These S/N aircraft have AAC Option No. 93 incorporated into the production aircraft. (3) AAC Option No. 93 extends each wing tip 15 in ches and increases the permissible maximum weight from 5700 lbs. to 6000 lbs. (4) The maximum weight of these S/N aircraft may be increased to 6000 lbs. when modified in accordance with AAC Option No. 93. (5) For aircraft equipped for Flight into known Icing (AAC Option No. 196). (6) For aircraft with Aerostar Ki t 764 969V (ventral rudder) installed. Empty Weight None C.G. Range Maximum Weight 6025 lbs. MAX RAMP (S/N 61-0838-8162152 and subsequent) 6000 lbs. MAX TAKEOFF (S/N 61-0342-112 and subsequent) 5700 lbs. MAX TAKEOFF (S/N 61-0001 thru 61-0334-111and 62-001)* All weight over 5900 lbs. must be fuel in the wing. *The maximum weight of these S/N airc raft may be increased to 6000 lbs. when modified in accordance with AAC Option No. 93 which extends each wing tip 15 inches No. of seats Crew or Fuselage Passenger Station 2 96 (CREW) 2 132 2 165* *When bench seat is fitted, thr ee occupants may be accommodated provided the the maximum weight of 380 lbs. is not exceeded. See Flight Manual for loading i n s t r u c t i o n s . A17WE 6 Maximum Baggage (See Note 2) Rear Compartment 240 lbs. at (+245) Fuel Capacity Wing Total Capacit y (65 gals. each).......... 130 gals Wing Total Usable (62 gals. each)............ 124 gals Fuselage Total C apacity.............................. 43.5 gals Fuselage Total Usable................................ 41.5 gals Aircraft Total Capacity................................... 173. 5 gals Aircraft Tota l Usable................................... 165.5 gals (See Note1 for unusable fuel) Oil Capacity Total Capacity two engines @ sta. +145.. 24 qts. Capacity each engine @ st a. +145............ 12 qts. Usable each engi ne..................................... 9 1/4 qts. (See Note 1 for undrainable oil) Maximum Operating Altitude 30,000 feet Control Surface Movement Wing Flaps* Down 45 °+ 3° Main Surfaces Aileron** Up 25° + 1° Down 15° + 1° Elevator Up 30° + 1° Down 10° + 1° Rudder Right 30° + 1° Left 30° + 1° ***Right 35° +1° - 0 ° Tabs (Main surface in neutral) Elevator Up 7°+ 1° Down 37° +9° - 1 ° Rudder Right 9° + 4° Left 37° + 4° - 1 ° -1° *Flaps must be rigged so that at 20° flap se tting, R.H. flap must not be more than 1.0° lower or 4.0° above the L.H. flap. **Ailerons are rigged 2° down. Movements are measured from this neutral position. Elevator and rudder movements are measured from a faired neutral position. ***For aircraft with Aerostar Kit 764 969V (ventral rudder) installed. Serial Numbers Eligible 61-0001 thru 61-0002-19 thru 61-0070-129, 61-0132-071 thru 61-0880-8162157, 60-82620001 and subsequent and 62-0001-013. (See Note 4) III Aerostar Model PA-60-601P (AEROSTAR 601P) (Normal Category) Approved November 14, 1973 (See Note 2, 3, and 4) Engines Two Lycoming IO-540-P1A5, IO-540-S1A5 m odified to incorporate automatic controlled turbochargers in accordance with RAJAY ST C SE60WE with Bendix fuel injector servos 2524477- for S/N 61P-0157-001 thru 61P-0211-021* and 2524491- for S/N 61P-0213-022 thru S/N 61P-0455-176** o r Two Lycoming IO-540-P1A5, IO-540-S1A5 modifi ed to incorporate automatic controlled turbochargers in accordance with AEROSTAR ST C SE81WE with Bendix fuel injector servos 2524491- for S/N 61P-0456-177 and subsequent. 7 A17WE *These aircraft require P/N 2524491 Bendix fuel injector servos when modified in accordance with AAC Option 93. **These aircraft incorporate turbochargers per AAC STC SE81WE when modified in accordance with AAC Option 155. Fuel 100/130 and 100LL minimum grade aviation gasoline Engine Limits *2575 RPM, 29.5 in. Hg. MAP (290 HP) for all operations. **2575 RPM, 29.5 in. Hg. MAP (290 HP) Maximum Continuous Power for takeoff, obstacle clearance, and emergency operati ons only. (No time limit). 2475 RPM, 29.5 in. Hg. MAP (278 HP) Maximum Normal Operating Power for noise certification and for all other operations. (No time limit) (See "Noise Characteristics" paragraph). *For S/N 61P-0157-001 thru 61P-0714-7963345 **For S/N 61P-0715-8063346 and subsequent Propeller Two Hartzell full-feathering propellers - HC-C3YR-2/C8468-8R or HC-C3YR-2UF/FC8468-8R Propeller Limits a.) Pitch settings at 30 in. sta. Low 14°+ 0.1°, High 18°-21° Feather 82.5°+ 1.0° Diameter: 78 inches No cutoff for repairs permitted b.) Spinners - Hartzell C-3258P c.) Propeller Governor - Hartzell F-6-5A, F-6- 35, F-6-35Z, F-6-36, F-6-36Z, F-8-35, F-8-35Z, F-8- 45, F-8-45Z. NOTE: If modified in accordance with AAC Option 64, Synchrophaser, Governor for right engine is F-8-35 or F-8-35Z. If modified in accordance with AAC Option 150, Synchrophaser, Governor for right engine is F-8-45 or F-8-45Z. Airspeed Limits (See Note 2) V ne- Never exceed 243 KCAS (280 MPH) V no- Max. structural cruising 217 KCAS (250 MPH) Reduce V ne and Vno (5 MPH) 4 knots for each 1,000 feet above 24,000 feet. V a- Max. design maneuvering 163 KCAS (188 MPH) V fe- *Flaps extended 20° 156 KCAS (180 MPH) 45° 130 KCAS (150 MPH) - **Flaps extended 20° 174 KCAS (200 MPH) 45° 149 KCAS (172 MPH) V le-Max. gear extended 156 KCAS (180 MPH) V lo-Max gear retraction 130 KCAS (150 MPH) -Max gear extension 156 KCAS (180 MPH) *For S/N 61P-0157-001 thru 61P -0354-109. The flap speeds for these S/N aircraft may be increased from 150 MPH CAS and 180 MPH CAS to 172 MPH CAS and 200 MPH CAS respectively when modified in accordance with AAC Option No. 131. **For S/N 61P-0356-128 and subsequent. A17WE 8 C. G. Range LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 lbs. 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (6) 61P-0157-001 thru 4600 157.66 (12.2% MAC) 167.88 ( 28.5% MAC) 61P-0211-021; 5700 160.03 (15.7% MAC) 167.88 (28.5% MAC) 5700 160.03 (15.7% MAC) 166. 00 (25.5% MAC) (5) (4) (6) 4600 157.66 (12.2% MAC) 166.00 (25.5% MAC) (6) 61P-0213-022 thru 4600 157.66 (12.2% MAC) 167.88 ( 28.5% MAC) 61P-0825-8063433; LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 6000 160.67 (17% MAC) 167.88 (28.5% MAC) 6000 160.67 (17% MAC) 166.00 (25.5% MAC) (5) (2) (6) 4600 lbs. 157.66 (12.2% MAC) 166.00 (25.5% MAC) (6) 61P-0826-8163434 4600 157.66 (12.2% MAC) 167.88 ( 28.5% MAC) and subsequent 6000 160.67 (17% MAC) 167.88 (28.5% MAC) 6025 160.72 (17.1% MAC) 167.88 (28.5% MAC) 6000 160.67 (17% MAC) 166.00 (25.5% MAC) (5) (6) 6025 160.72 (17.1% MAC) 166.00 (25.5% MAC) (5) (6) (1) Straight line va riation between points. (2) These S/N aircraft have AAC Option No. 93 incorporated into the production aircraft (3) AAC Option No. 93 extends each wing tip 15 in ches and increases the permissible maximum weight from 5700 lbs. to 6000 lbs. (4) The maximum weight of these S/N aircraft may be increased to 6000 lbs. when modified in accordance with AAC Option No. 93. (5) For aircraft equipped for Flight In to Known Icing (AAC Option No. 196). (6) For aircraft with Aerostar Ki t 764 969V (ventral rudder) installed. Empty Weight None C.G. Range Maximum Weight 6025 lbs. MAX RAMP (S/N 61P-0826-8163434 and subsequent) 6000 lbs. MAX TAKEOFF (S/N 61P-0213-022 and subsequent) 5700 lbs. MAX TAKEOFF (S/N 61P-0157-001 thru 61P-0211-021)* All weight over 5900 lbs. must be fuel in the wing. *The maximum weight may be increased from 5700 lbs. to 6000 lbs. when modified in accordance with AAC Option No. 93 which extends each wing tip 15 inches. Number of Seats Crew or Fuselage Passenger Station 2 9 6 ( c r e w ) 2 132 2 165* *When bench seat is fitted, three occupants may be accommodated provided that the maximum weight of 380 lbs. is not exceeded. See Flight Manual for loading instructions. 9 A17WE Maximum Baggage (See Note 2 ) Rear compartment 240 lbs. at (+245). Fuel Capacity Wing Total Capacit y (65 gals. each).......... 130 gals Wing Total Usable (62 gals. each)............ 124 gals Fuselage Total C apacity.............................. 43.5 gals Fuselage Total Usable................................. 41. 5 gals Aircraft Total C apacity................................ 173.5 gals Aircraft Tota l Usable................................. 165.5 gals (See Note 1 for unusable fuel) Oil Capacity Total Capacity two engines @ sta. +145... 24 qts Capacity each engine @ sta. +145............ 12 qts Usable each engi ne................................... 9 1/4 qts (See Note 1 for undrainable oil) Maximum Operating Altitude 25,000 feet (30,000 feet when equipped with AAC Option 262, and 264.) Maximum Cabin Operating Pressure 4.25 PSI (5.50 PSI when equipped with AAC Option 262.) Control Surface Movement Wing Flaps* Down 45 °+ 3° Main Surfaces Aileron** Up 25° + 1° Down 15° + 1° Elevator Up 30° + 1° Down 10° + 1° Rudder Right 30° + 1° Left 30° + 1° ***Right 35° + 1° - 0 ° Tabs (Main surface in neutral) Elevator Up 7°+ 1° Down 37° +9° - 1 ° Rudder Right 9° +4° Left 37° +4° - 1 ° - 1 ° *Flaps must be rigged so that at 20° flap setting, the R.H. flap must not be more than 1.0° lower or 4.0° above the L.H. flap. **Ailerons are rigged 2° down. Movements are measured from this neutral position. Elevator and rudder mo vements are measured from a faired neutral position. ***For aircraft with Aerostar Kit 764 969V (ventral rudder) installed Serial Numbers Eligible 61P-0157-001 thru 61P-0860-8163455, 60-8263001 and subsequent. (See Note 4) IV - Aerostar Model PA-60-602P (AEROSTAR 602P) (Normal Category) Approved October 30,1980 (See Note 2, 3, & 4) Engines Two Lycoming IO-540-AA1A5 engines incorpor ating Bendix fuel injector servos Bendix P/N 2524846-1 and automatically controlled tur bochargers Aerostar Kits P/N 300076-515 (LH engine) and P/N 300076-517 (RH engine). Fuel 100/130 and 100LL minimum grade aviation gasoline. Engine Limits 2425 RPM, 37 in. Hg. MAP (290 HP) for all operations. Propeller Two Hartzell full-feathering propellers - HC-C3YR-2UF/FC8468-8R, or HC-C3YR-2/C8468-8R A17WE 10 Propeller Limits a.) Pitch settings at 30 in. sta. Low 15.9°+ 0.1°, High 18°-21° Feather 82.5°+ 1.0° Diameter: 78 in. No cutoffs for repairs permitted b.) Spinners - Hartzell C-3258P c.) Propeller Governor - Hartzell F-6-60Z, F-8-60Z. NOTE: If Modified in accordance with AAC Option #150, Synchrophaser, Governor for right engine is F-8-60Z. Airspeed Limits (See Note 2) (KCAS). V ne- Never exceed 243 KCAS (280 MPH) V no- Max. structural cruising 217 KCAS (250 MPH) Reduce V ne and Vno (5 MPH) 4 knots for each 1,000 feet above 24,000 feet. V a- Max. design maneuvering 167 KCAS (192 MPH) V fe- *Flaps extended 20° 174 KCAS (200 MPH) 45° 149 KCAS (172 MPH) V le-Max. gear extended 156 KCAS (180 MPH) V lo-Max gear retraction 130 KCAS (150 MPH) -Max gear extension 156 KCAS (180 MPH) C. G. Range LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 lbs. 157.66 (12.2% MAC) 166.00 (25.5% MAC) 62P-0750-8165001, 6000 160.67 (17% MAC) 166.00 ( 25.5% MAC) 62P-0861-8165002 6029 160.72 (17.1% MAC) 166.00 ( 25.5% MAC) and subsequent (1) Straight line va riation between points. Empty Weight None C.G. Range Maximum Weight 6029 lbs. MAX RAMP 6000 lbs. MAX TAKEOFF Number of Seats Crew or Fuselage Passenger Station 2 9 6 ( c r e w ) 2 132 2 165* *When bench seat is fitted, three occupants may be accommodated provided that the maximum weight of 380 lbs. is not exceeded. See Flight Manual for loading instructions. Maximum Baggage (See Note 2) Rear compartment 240 lbs. at (+245). 11 A17WE Fuel Capacity Wing Total Capacit y (65 gals. each).......... 130 gals Wing Total Usable (62 gals. each)............ 124 gals Fuselage Total C apacity.............................. 43.5 gals Fuselage Total Usable................................. 41. 5 gals Aircraft Total C apacity................................ 173.5 gals Aircraft Total Usable................................. 165. 5 gals (See Note 1 for unusable fuel) Oil Capacity 12 qts. per engine (9.25 qts. per engine usable) (See Note 1 for undrainable oil). Maximum Operating Altitude 25,000 feet (30,000 feet when equipped with AAC Options 262, and 264.) Maximum Cabin